Multiple quick disconnector



March 13, 1962 c. P. HEROLD 3,024,703

MULTIPLE QUICK DISCONNECTOR Filed Feb. 12, 1959 3 Sheets-Sheet 1 Curi' P Herold Fig. l- BY March 13, 1962 c. P. HEROLD MULTIPLE QUICK DISCONNECTOR 3 Sheets-Sheet 2 Filed Feb. 12, 1959 Curt P Herold,

March 13, 1962 c. P. HEROLD 3,024,703

MULTIPLE QUICK DISCONNECTOR Filed Feb. 12, 1959 3 Sheets-Sheet 3 states free 3,024,703 MULTIPLE QUICK DISCONNECTOIR Curt I. Herold, 800 Carmelin Drive SE,

Huntsville, Ala. Filed Feb. 12, 1959, Ser. No. 792,926 2 Claims. (Cl. 89-13) (Granted under Title 35, U.S. Code (1952), sec. 266) The invention described herein may be manufactured and used by or for the Government for governmental purposes Without the payment of any royalty thereon.

My invention relates to means for connecting missiles erected on launching pads with sources of supply and external testing instruments, and more particularly to a unitary connector for disconnecting the conduits from the missiles at the time of firing thereof.

Conventionally, final testing of the missiles is 6011- ducted while the missiles are mounted on the launching pads and electrical energy for the testing is provided from sources external to the missiles. Also, certain compartments of the missiles are supplied with refrigerant from external sources thereof while the missiles are erected on the launching pads.

Since the circuits to be supplied and tested and the compartments to be refrigerated are disposed adjacent the forward ends of the missiles, considerable weight thereof is saved by employment of conduits external to the missiles to enclose wires for the electrical supply and testing, and to conduct refrigerant to the compartments to be cooled.

The conduits are disconnected from the missiles responsive to firing for unfettered launching thereof.

An object of my invention is to provide a unitary connector for releasably connecting conduits to the missiles.

Another object of my invention is to provide such a connector disposed to disconnect the conduits from the missiles responsive to firing thereof.

A further object of my invention is to provide such a connector with a pivoted mast tilted away from the missiles for rotation therefrom responsive to release.

Other aims and objects of my invention will appear from the following explanation.

In carrying out my invention, connectors for removably securing conduits to missiles are respectively provided with terminal and plate members with corresponding parts of couplings secured thereto for respective attachment to the conduits and the missiles. The coupling parts are slidable to complete connection therebetween responsive to engagement of the members and a device with radiallydisplaceable balls and a resistance link is disposed between the members to secure the connection and to release the members responsive to firing the missiles.

The terminal members include spring biased plungers to engage the plate for disengagement of the coupling parts responsive to the release.

A mast is pivoted on the launching pad of the missile to support the conductor releasably secured to the missile for rotation therefrom at launching. A storage container for refrigerant is disposed on the mast adjacent the terminal to reduce the length of conduit leading from the container.

For more complete understanding, reference is directed to the following description and the accompanying drawing, in which:

FIGURE 1 is an elevation of a missile supported on a launching pad with a pivoted mast thereof secured to the missile by a connector;

FIGURE 2 is a diminished view similar to FIGURE 1 with the mast disconnected from the missile;

FIGURE 3 is an enlarged view of the connector with the housing secured to the plate; and

FIGURE 4 is a view similar to FIGURE 3 with the housing disengaged from the plate.

Accordingly, a missile 12 is disposed on a launching pad 14 and a connector 16 is provided for securing conduits 18 to missile 12. Connector 16 includes a plate 20 secured to the surface portion of missile l2 and a terminal 22 with a housing 24 having a base 26. Base 26 is secured to a mast 56 pivoted at 58 on pad 14.

Couplings 28 each includes parts 30 and 32 respectively secured in plate 20 and base 26, and housing 24 is disposed for engagement with plate 20 for parallel relation of base 26 therewith, and slidable engagement of the corresponding parts of the couplings to complete connection of the conduits to the missile.

Connector 16 includes a latch mechanism 33 with a ring 34 disposed in plate 20 and a cylindrical member 36 disposed for engaging ring 34 includes radial holes 38 with balls 40 therein.

A rod 42 is axially disposed in member 36 for slidable axial operation to a cocked position in engagement with balls 40 for radial displacement thereof to respective simultaneous engagement with holes 38 and a semi-toroidal groove 44 in ring 34 to secure terminal 22 to plate 20.

A lock mechanism 45 is provided with a lever 46 pivoted at 48 on terminal 22 and retained in a closed position by an electrical resistance link 50 secured to terminal 22 to retain rod 42 in the cocked position. The rod is biased to a normal position out of engagement with the balls by a spring 52. Link 50 is disposed for application of a current thereto to release terminal 22 from plate 20 responsive to firing of the missile.

Plungers 54 are biased from terminal 22 by springs 55 for engagement of the plungers with plate 20 for separation of. parts 30 and 32 of the couplings responsive to the release.

As shown in FIGURE 1 missile 12 is erected on pad 14 for launching. Mast 56 is angled outward from missile 12 for rotation therefrom responsive to release of terminal 22 from plate 20 for rotation of the mast from the missile. Mast 56 is disposed to enclose conduits 18 for protection thereof, and a container for storage, such as a refrigerant storage container 60 is disposed on mast 56 adjacent terminal 22 to limit the length of conduit 18 leading therefrom.

As shown in FIGURE 3 the mechanical advantage of lever 46 is high to require low tensile strength of link 50 for retention of the link in the closed position. Conductors 62 and 64 connect link 59 to a separate source of electrical energy for application thereto of the value of current required to fuse the link.

While the foregoing is a description of the preferred embodiment, the following claims are intended to include those modifications and variations that are within the spirit and scope of my invention.

I claim:

1. Apparatus for servicing and launching a missile comprising: a pad for support of said misile; pivot means mounted on said pad; a mast having the lower end thereof attached to said pivot means for pivoting on said pivot means; conduits extending through said mast for servicing said missile; a terminal secured to said conduits and said mast; a plate attached to said missile, said plate and said terminal being in engagement to complete communication of said conduits with the missile; means attached to said terminal for disengaging said terminal from said plate; and ejection means connected to said terminal for providing a force to pivot said mast from the missile responsive to the disengagement of said terminal from said plate.

2. A device as set forth in claim 1 wherein said ejecforce to pivot said mast from the missile comprises a plurality of spring-actuated plungers.

References Cited in the file of this patent UNITED STATES PATENTS OTHER REFERENCES Tele-Tech & Electronics Industries, May 1954, Guided Missile by Leslie Baird and Harlan Upston, pp. 70, 71, 129, 130 and 131. Copy in Div. 20.

Ordnance, vol. XLII, MarchApril 1958, No. 2,

tion means connected to said terminal for providing a 15 Launching our First sa'wllite, P 

